Encyclopedia Astronautica
RD-0140


Kosberg Lox/LNG rocket engine. 2086 kN. stage 2. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Gas generator cycle with turbine gas injection into supersonic nozzle. Isp=349s.

Application: stage 2.

Engine: 1,689 kg (3,723 lb). Thrust to Weight Ratio: 125.93.

Status: Developed 1998-on.
Unfuelled mass: 1,689 kg (3,723 lb).
Height: 5.04 m (16.53 ft).
Thrust: 2,086.00 kN (468,951 lbf).
Specific impulse: 349 s.
Specific impulse sea level: 300 s.
First Launch: 1998-.

More... - Chronology...


Associated Countries
See also
Associated Manufacturers and Agencies
  • Kosberg Russian manufacturer of rocket engines. Kosberg Design Bureau, Russia. More...

Associated Propellants
  • Lox/LNG Liquid oxygen was the earliest, cheapest, safest, and eventually the preferred oxidiser for large space launchers. Its main drawback is that it is moderately cryogenic, and therefore not suitable for military uses where storage of the fuelled missile and quick launch are required. Liquefied natural gas - mainly methane,with traces of sulfur, etc. More...

Bibliography
  • Novosti kosmonavtiki, Issue 3, 1999.

Home - Browse - Contact
© / Conditions for Use